Heat Flux Gage Studies of Compressible Dynamic Stall
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Authors
Chandrasekhara, M.S.
Wilder, M.C.
Subjects
Advisors
Date of Issue
2002-01
Date
January 14-17, 2002
Publisher
Language
Abstract
Compressible dynamic stall was studied using 148 closely
spaced heat flux gages distributed over the surface of an
oscillating, 6-inch chord NACA 0012 airfoil. The study has
revealed the various surface flow features of compressible
dynamic stall and their changes under different flow
conditions. It has also provided a description of the events
that are precursors to dynamic stall onset. The imprint of a
leading edge shock has been recorded for the first time in
the surface flow signature. The data indicate that extremely
large gradients develop prior to onset of dynamic stall,
pointing to a singular event that drives the flow into the
stalled state.
Type
Conference Paper
Description
The article of record as published may be found at http://dx.doi.org/10.2514/6.2002-291
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Army Research Office under grant no. MIPROKNPGAS052
Funder
Army Research Office under grant no. MIPROKNPGAS052
Format
8 p.
Citation
40th AIAA Aerospace Sciences
Meeting and Exhibit
January 14-17, 2002 / Reno, NV
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.